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Wake Geometry Measurements and Analytical Calculations on a Small-Scale Rotor ModelAn experimental investigation was conducted in the Langley 14- by 22-Foot Subsonic Tunnel to quantify the rotor wake behind a scale model helicopter rotor in forward level flight at one thrust level. The rotor system in this test consisted of a four-bladed fully articulated hub with blades of rectangular planform and an NACA 0012 airfoil section. A laser light sheet, seeded with propylene glycol smoke, was used to visualize the vortex geometry in the flow in planes parallel and perpendicular to the free-stream flow. Quantitative measurements of wake geometric proper- ties, such as vortex location, vertical skew angle, and vortex particle void radius, were obtained as well as convective velocities for blade tip vortices. Comparisons were made between experimental data and four computational method predictions of experimental tip vortex locations, vortex vertical skew angles, and wake geometries. The results of these comparisons highlight difficulties of accurate wake geometry predictions.
Document ID
19970001461
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Authors
Ghee, Terence A. (Analytical Services and Materials, Inc. Hampton, VA United States)
Berry, John D. (Army Aviation Systems Command Hampton, VA United States)
Zori, Laith A. J. (Iowa State Univ. of Science and Technology Ames, IA United States)
Elliott, Joe W. (Army Aviation Systems Command Hampton, VA United States)
Date Acquired
September 6, 2013
Publication Date
August 1, 1996
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
NAS 1.60:3584
ATCOM-TR-96-A-007
NASA-TP-3584
L-17449
Accession Number
97N11274
Funding Number(s)
PROJECT: RTOP 505-59-39-01
PROJECT: DA Proj. 1L1-62211-A-47-A
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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